三翼面验证机纯电方案设计  

Design of fully electric scheme for three-surface verification aircraft

作　　者：孔垂欢 吴大卫 谭兆光 潘立军 马茹冰 司江涛 Chuihuan KONG;Dawei WU;Zhaoguang TAN;Lijun PAN;Rubing MA;Jiangtao SI(Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China,Ltd.,Shanghai 201210,China)

机构地区：[1]中国商用飞机有限责任公司上海飞机设计研究院,上海201210

出　　处：《航空学报》2024年第6期104-114,共11页Acta Aeronautica et Astronautica Sinica

摘　　要：随着碳排放政策日趋严格,航空绿色出行成为民机设计新目标之一,传统布局的民航客机气动效率、结构效率提升空间有限,很难实现大幅减阻,采用新布局结合新能源的设计方案,成为当下研究的热点。本文总结了翼身融合(BWB)、桁架支撑翼(TBW)、三翼面(TSA)的新布局以及纯电为代表的新能源技术研究进展,基于“乘风2.0”200 kg级无人飞行验证机的布局特征,采用计算流体力学(CFD)和工程估算开展了三翼面布局气动特性分析和布局收益评估,分析了前翼与尾翼单独偏转和组合偏转力矩特性,前翼在大迎角具有较好的推杆改出和操纵能力;验证机完整的三翼面布局,相对于其取消前翼的布局,在4°迎角可获得约7%配平升力收益,考虑前翼方案带来的零阻、下洗、增重不利影响,仍可获得19.7count减阻收益,巡航升阻比提升3%;前翼+尾翼部件导致全机增重约0.3%;给出了分布式动力推进架构,该架构可减小90%不对称推力力矩;基于无人飞行验证机开展纯电动力架构和性能的飞行试验,得到了验证机45 m/s巡航所需功率约20 kW,巡航能耗为0.126 kW·h/km,35 m/s巡航所需功率8 kW,巡航能耗为0.065 kW·h/km;最大功率出现在起飞阶段为45 kW,是巡航功率的2倍,起飞能耗在飞行剖面占比约2%。With the increasingly strict carbon emission policy,green air travel has become one of the new goals of civil aircraft design.The room of improvement of aerodynamic efficiency and structural efficiency of the civil aircraft with traditional layout is limited,so it is difficult to achieve greater drag reduction.The design scheme of new layout combined with new energy have become a research hotspot.This paper summarizes the research progress of new layout technologies of Blended Wing Body(BWB),Truss-Braced Wing(TBW) and Three-Surface Aircraft(TSA),as well as new energy technologies of electric vehicles.Based on the layout characteristics of the 200 kg UAV verification aircraft “Windrider 2.0”,the aerodynamic characteristics analysis and layout benefit evaluation of the three-surface layout are carried out by the Computational Fluid Dynamics(CFD) and engineering estimation method.The pitching moment characteristics of single deflection and combined deflection of canard and horizontal tail are analyzed.The canard has the ability to recover from high angle of attack and good high-a nose-down control capability.Compared with the non-canard wing layout,the complete three-surface layout of the verification aircraft can obtain about 7% trim lift increase at 4° of angle of attack.Considering the negative effects of zero-lift drag,downwash and weight increase of the canard,the drag can be reduced by about 19.7count,and the cruise lift-to-drag ratio is increased by 3%.The take-off weight gain caused by the canard + tail components is about 0.3%.The distributed electric propulsion architecture is designed,which can reduce the asymmetric thrust moment by 90%.The flight test of electric propulsion architecture and performance is carried out based on the UAV verification aircraft.When the cruise airspeed is 45 m/s,the power required by the verification aircraft is about 20 kW,and the cruise energy consumption is 0.126 kW·h/km.When the cruise airspeed is 35 m/s,the power required is 8 kW,and the cruise energy consumption is

关 键 词：无人验证机 新布局 三翼面 纯电飞机 分布式电推进 

分 类 号：V217.3[航空宇航科学与技术—航空宇航推进理论与工程]